Cooling structure, heat insulating tile and combustion chamber based on staggered counterflow and rib turbulation

Abstract

The utility model discloses a kind of cooling structure based on staggered phase direction flow and rib turbulences, heat insulation tile and combustion chamber, cooling structure includes the cooling structure hot wall of facing high temperature and the cooling structure cold wall of facing low temperature, multiple first cooling channels and multiple interval distribution second cooling channels being parallel and immediately side-by-side arranged are equipped between cooling structure hot wall and cooling structure cold wall, every second cooling channel is broken line channel and is successively worn in multiple first cooling channels, the segment of each second cooling channel in every first cooling channel is formed rib turbulence structure by cooperation;Cooling gas in adjacent two first cooling channels flows reversely, and cooling gas in adjacent two second cooling channels flows reversely.The cooling structure can improve the cooling efficiency of cooling structure hot wall, and can ensure the temperature uniformity of entire cooling structure hot wall, and the cooling structure can greatly reduce the size requirement in thickness direction.

Description

Technical Field

[0001] This utility model belongs to the field of gas turbine technology, specifically relating to a cooling structure, heat insulation tiles, and combustion chamber based on staggered countercurrent flow and rib turbulence. Background Technology

[0002] As gas turbine performance continues to improve, the inlet pressure, inlet temperature, and outlet temperature of the combustion chamber gradually increase. This leads to increasingly stronger heat radiation from the flame to the combustion chamber bearings. The inlet temperature of the combustion chamber is the outlet air temperature of the compressor in the gas turbine. Since the compressor outlet air is also used for bearing cooling, the temperature of the cooling air continues to rise. Furthermore, the continuous improvement in gas turbine performance results in a decreasing amount of air available for bearing cooling at the compressor outlet. Therefore, the issue of thermal protection for the combustion chamber bearing surface becomes increasingly severe and important. Specifically, improving the overheating phenomenon of the combustion chamber bearings plays a crucial role in the safe and stable operation of the gas turbine. It directly affects not only the gas turbine's own operating performance parameters but also the unit's maintenance and service costs, and the frequency of unit maintenance. The frequency of gas turbine unit maintenance, in turn, impacts the economic indicators of the power plant. The above problems can be solved in two ways: one is to increase the allowable operating temperature of the tile material; the other is to strengthen the cooling protection of the tile and improve the utilization rate of cooling air.

[0003] Currently, the cooling method for heat insulation tiles used in the combustion chamber of gas turbines is mainly impact cooling. Although impact cooling has high cooling efficiency, it consumes a large amount of cooling air and has a small coverage area, which easily leads to uneven temperature distribution in the heat insulation tiles. This results in insufficient cooling, and during operation, insufficient cooling can cause localized failure of the heat insulation tiles. Therefore, designing a highly efficient and uniform cooling structure suitable for heat insulation tiles is of great significance.

[0004] Patent CN120140797A discloses a heat insulation tile and heat shield with staggered cooling channels for a combustion chamber, including a hot sidewall and an outer edge connected to its perimeter; a cold sidewall is disposed on one side of the hot sidewall and connected to the outer edge, the hot sidewall, the outer edge, and the cold sidewall forming a chamber; multiple transverse cooling channels are longitudinally spaced on the cold surface of the hot sidewall, one end of each transverse cooling channel penetrates the outer edge, and the other end communicates with the chamber, with the cooling gas flowing in opposite directions in adjacent transverse cooling channels; multiple longitudinal cooling channels are transversely spaced inside the hot sidewall, one end of each longitudinal cooling channel penetrates the outer edge, and the other end communicates with the chamber, with the cooling gas flowing in opposite directions in adjacent longitudinal cooling channels. In this patent, the cooling channel structure within the heat insulation tile is simple, and the longitudinal cooling channels are located far from the surface to be cooled, resulting in a much weaker cooling effect than the transverse cooling channels. Therefore, the overall cooling effect of the heat insulation tile in this patent is generally poor. Furthermore, the arrangement of the transverse and longitudinal cooling channels imposes certain requirements on the thickness of the heat insulation tile.

[0005] Patent CN118242668A discloses a combustion chamber tile, including a tile body with a first surface and a second surface arranged opposite to each other. The tile body also contains a first cooling layer near the first surface and a second cooling layer near the second surface. The first cooling layer includes a plurality of first cooling channels spaced apart along a first side of the tile body, and the second cooling layer includes a plurality of second cooling channels spaced apart along a second side of the tile body. The first and second cooling channels are one or more of the following: V-shaped rib channels, bent channels, bamboo-joint channels, annular channels, and recessed channels. In this patent, the second cooling layer within the combustion chamber tile is also located far from the surface to be cooled, and its cooling effect is much weaker than that of the first cooling layer. Therefore, the overall cooling effect of the combustion chamber tile in this patent is generally poor. Furthermore, the arrangement of the first and second cooling layers imposes certain requirements on the thickness of the combustion chamber tile. Utility Model Content

[0006] In view of the above-mentioned defects of the prior art, the present invention provides a cooling structure, heat insulation tile and combustion chamber based on staggered phase flow and rib turbulence. The cooling structure can improve the cooling efficiency of the hot wall of the cooling structure, ensure the temperature uniformity of the hot wall of the entire cooling structure, and greatly reduce the dimensional requirements in the thickness direction.

[0007] The technical solution adopted by this utility model to solve its technical problem is:

[0008] A cooling structure based on staggered countercurrent flow and ribbed turbulence includes a hot wall facing high temperature and a cold wall facing low temperature. The first ends of the hot wall and the cold wall are connected by a first outer edge wall, and the second ends of the hot wall and the cold wall are connected by a second outer edge wall opposite to the first outer edge wall. Multiple parallel and adjacent first cooling channels and multiple spaced second cooling channels are provided between the hot wall and the cold wall. One end of each first cooling channel is located at the third end of the hot wall and the cold wall, and the other end is located at the fourth end of the hot wall and the cold wall. Each second cooling channel is a zigzag channel and is sequentially inserted within the multiple first cooling channels. The segments of each second cooling channel within each first cooling channel cooperate to form a ribbed turbulence structure. The cooling gas in two adjacent first cooling channels flows in opposite directions, and the cooling gas in two adjacent second cooling channels flows in opposite directions as well.

[0009] Furthermore, each segment of the second cooling channel within each of the first cooling channels is a zigzag rib, and each second cooling channel is tightly attached to the hot wall of the cooling structure.

[0010] Furthermore, each segment of the second cooling channel within each of the first cooling channels is a V-shaped zigzag rib.

[0011] Furthermore, the V-shaped openings of each V-shaped rib within each of the first cooling channels are oriented towards the direction of cooling gas flow within the corresponding first cooling channel.

[0012] Furthermore, the orthographic projection of the vertex of each V-shaped rib within each of the first cooling channels lies on the central axis of the corresponding first cooling channel.

[0013] Furthermore, the opening size of each of the first cooling channels is equal, the opening size of each of the second cooling channels is equal, and the plurality of second cooling channels are distributed at equal intervals.

[0014] A heat-insulating tile for a combustion chamber in a gas turbine includes a heat-insulating tile hot wall facing the flame inside the combustion chamber and a heat-insulating tile cold wall facing the combustion chamber shell. The outer edge of the heat-insulating tile hot wall is connected to a first outer peripheral wall for facing the combustion chamber shell, and the outer edge of the heat-insulating tile cold wall is connected to a second outer peripheral wall for facing the combustion chamber shell. The ends of the first and second outer peripheral walls facing the combustion chamber shell are connected by a connecting wall. The first outer peripheral wall, the second outer peripheral wall, the heat-insulating tile hot wall, and the connecting wall form a cooling gas chamber.

[0015] It also includes the aforementioned cooling structure based on staggered countercurrent flow and rib turbulence, wherein the cooling structure is arranged between the hot wall and cold wall of the heat insulation tile, and the hot wall of the heat insulation tile forms the hot wall of the cooling structure, and the cold wall of the heat insulation tile forms the cold wall of the cooling structure. One end of each first cooling channel is connected to the cooling gas chamber and the other end is connected to the outside through the first outer peripheral wall. One end of each second cooling channel is connected to the cooling gas chamber and the other end is connected to the outside through the first or second outer peripheral wall.

[0016] Furthermore, there are two heat-insulating tile cold walls distributed at a certain distance, and each heat-insulating tile cold wall is connected to a second outer peripheral wall. The connecting wall is connected to the first outer peripheral wall and the two second outer peripheral walls. There are two cooling structures, and each cooling structure is arranged between the heat-insulating tile hot wall and one of the heat-insulating tile cold walls.

[0017] Furthermore, it also includes a hollow fastening housing with one open end. The open end of the fastening housing is connected to the corresponding positions of the two heat insulation tile cold walls, the two second outer peripheral walls, and the connecting wall. The inner cavity of the fastening housing is in communication with the cooling gas chamber. The fastening housing is provided with heat insulation tile mounting holes for oriented towards the combustion chamber housing. One end of the heat insulation tile mounting holes penetrates the heat insulation tile hot wall, and the other end penetrates the shell wall of the fastening housing for being adjacent to the combustion chamber housing. The shell wall of the fastening housing is provided with an air inlet.

[0018] A combustion chamber for a gas turbine includes a combustion chamber shell and the aforementioned heat insulation tile for the combustion chamber in a gas turbine, wherein the heat insulation tile is fixed to the combustion chamber shell by fastening screws passing through mounting holes in the heat insulation tile.

[0019] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0020] The present invention relates to a cooling structure based on staggered countercurrent flow and ribbed turbulence, comprising a hot wall facing high temperature and a cold wall facing low temperature. The first ends of the hot wall and the cold wall are connected by a first outer edge wall, and the second ends are connected by a second outer edge wall opposite to the first outer edge wall. Multiple parallel and adjacent first cooling channels and multiple spaced second cooling channels are provided between the hot and cold walls. One end of each first cooling channel is located at the third end of the hot and cold walls, and the other end is located at the fourth end of the hot and cold walls. Each second cooling channel is a zigzag channel and is sequentially inserted within the multiple first cooling channels. The segments of each second cooling channel within each first cooling channel cooperate to form a ribbed turbulence structure. The cooling gases in adjacent first cooling channels flow in opposite directions, and the cooling gases in adjacent second cooling channels also flow in opposite directions. Because each second cooling channel is a zigzag channel, the cooling gas flow within each channel is tortuous, creating strong turbulence. This enhances heat exchange between the hot walls of the cooling structure and the cooling gas, improving the cooling efficiency of the hot walls. Furthermore, since each second cooling channel is sequentially inserted within multiple first cooling channels, the segments of each second cooling channel within the corresponding first cooling channel form a ribbed turbulence structure. Consequently, the cooling gas within each first cooling channel flows tortuously and creates strong turbulence under the influence of these second cooling channel segments, further enhancing heat exchange between the hot walls of the cooling structure and the cooling gas, and improving the cooling efficiency of the hot walls. Therefore, this cooling structure, through multiple second cooling channels... The arrangement of the channels creates a highly efficient turbulence structure that combines self-turbulence and external turbulence. Furthermore, because the cooling gases in two adjacent first cooling channels flow in opposite directions, and the cooling gases in two adjacent second cooling channels flow in opposite directions, this staggered flow pattern effectively ensures the temperature uniformity of the entire cooling structure's hot wall. In addition, since each second cooling channel is sequentially inserted into multiple first cooling channels, by embedding the second layer of cooling components formed by multiple second cooling channels into the first layer of cooling components formed by multiple first cooling channels, this cooling structure can greatly reduce the dimensional requirements in the thickness direction. At the same time, it allows the cooling gas to more uniformly approach the hot wall of the cooling structure that needs to be cooled. In addition, this cooling structure also fully cools the cold wall of the cooling structure. Attached Figure Description

[0021] Figure 1 This is a three-dimensional structural diagram of the cooling structure based on staggered countercurrent flow and rib turbulence in this utility model;

[0022] Figure 2 This is a three-dimensional internal structure diagram of the cooling structure based on staggered countercurrent flow and rib turbulence in this utility model;

[0023] Figure 3 This is a schematic diagram of the cooling gas flow direction within the cooling structure based on staggered phased flow and rib turbulence in this utility model;

[0024] Figure 4 for Figure 3 Schematic diagram of the cross-sectional structure along the AA direction;

[0025] Figure 5 This is a three-dimensional structural diagram of the heat insulation tile used in the combustion chamber of a gas turbine in this utility model, taken from one direction.

[0026] Figure 6 This is a three-dimensional structural diagram of the heat insulation tile used in the combustion chamber of a gas turbine in this utility model from another direction;

[0027] Figure 7 This is a first three-dimensional cross-sectional view of the heat insulation tile used in the combustion chamber of a gas turbine according to the present invention;

[0028] Figure 8 This is a second three-dimensional cross-sectional view of the heat insulation tile used in the combustion chamber of a gas turbine according to the present invention;

[0029] Figure 9 This is a third-dimensional cross-sectional view of the heat insulation tile used in the combustion chamber of a gas turbine according to the present invention.

[0030] Explanation of reference numerals in the figure: 1. Cooling structure, 101. Hot wall of cooling structure, 102. Cold wall of cooling structure, 103. First outer edge wall, 104. Second outer edge wall, 105. First cooling channel, 106. Second cooling channel, 2. Insulation tile, 201. Hot wall of insulation tile, 202. Cold wall of insulation tile, 203. First outer peripheral wall, 204. Second outer peripheral wall, 205. Connecting wall, 206. Cooling gas chamber, 207. Fastening shell, 20701. Inner cavity, 20702. Shell wall, 208. Insulation tile mounting hole, 209. Air inlet. Detailed Implementation

[0031] The specific embodiments of this utility model will be further described in detail below with reference to the accompanying drawings. These embodiments are only used to illustrate this utility model and are not intended to limit it.

[0032] In the description of this utility model, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this utility model. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0033] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0034] Furthermore, in the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0035] like Figures 1-4 As shown, a cooling structure based on staggered countercurrent flow and ribbed turbulence includes a hot wall 101 facing high temperature and a cold wall 102 facing low temperature. The first end of the hot wall 101 and the first end of the cold wall 102 are connected by a first outer edge wall 103. The second end of the hot wall 101 and the second end of the cold wall 102 are connected by a second outer edge wall 104 opposite to the first outer edge wall 103. Multiple parallel and adjacent first cooling channels 105 and multiple spaced-apart channels are provided between the hot wall 101 and the cold wall 102. The second cooling channel 106, one end of each first cooling channel 105 is located at the third end of the hot wall 101 and the cold wall 102 of the cooling structure, and the other end is located at the fourth end of the hot wall 101 and the cold wall 102 of the cooling structure. Each second cooling channel 106 is a zigzag channel and is sequentially arranged within multiple first cooling channels 105. The segments of each second cooling channel 106 within each first cooling channel 105 cooperate to form a ribbed turbulence structure. The cooling gas in two adjacent first cooling channels 105 flows in opposite directions, and the cooling gas in two adjacent second cooling channels 106 flows in opposite directions, see... Figure 3 .

[0036] Since each second cooling channel 106 is a zigzag channel, the cooling gas flow within each second cooling channel 106 is tortuous, thus creating strong turbulence. This enhances heat exchange between the cooling structure hot wall 101 and the cooling gas, and improves the cooling efficiency of the cooling structure hot wall 101. Furthermore, since each second cooling channel 106 is sequentially inserted within multiple first cooling channels 105, the segments of each second cooling channel 106 within each first cooling channel 105 cooperate to form a rib-like turbulence structure. Consequently, the cooling gas within each first cooling channel 105 flows tortuously and forms strong turbulence under the influence of the segments of each second cooling channel 106. Figure 4 This enhances the heat exchange between the hot wall 101 and the cooling gas, and improves the cooling efficiency of the hot wall 101. Therefore, the cooling structure 1, through the arrangement of multiple second cooling channels 106, can form a highly efficient turbulence structure combining self-turbulence and external turbulence. Furthermore, since the cooling gas in two adjacent first cooling channels 105 flows in opposite directions, and the cooling gas in two adjacent second cooling channels 106 flows in opposite directions, the temperature uniformity of the entire hot wall 101 can be effectively guaranteed by adopting a staggered flow pattern. In addition, since each second cooling channel 106 is sequentially inserted into multiple first cooling channels 105, by embedding the second layer of cooling components formed by multiple second cooling channels 106 into the first layer of cooling components formed by multiple first cooling channels 105, the cooling structure 1 can greatly reduce the dimensional requirements in the thickness direction, while allowing the cooling gas to more uniformly approach the hot wall 101 of the cooling structure that needs to be cooled. In addition, the cooling structure 1 will also fully cool the cold wall 102 of the cooling structure.

[0037] In addition, since each second cooling channel 106 is a zigzag channel and is sequentially arranged within multiple first cooling channels 105, the cooling structure 1 adopts an internal cooling method close to the cooling structure hot wall 101, and enhances the heat exchange between the cooling structure hot wall 101 and the cooling gas through a strong turbulence design, so that the cooling structure hot wall 101 has a high cooling efficiency. At the same time, the staggered flow pattern effectively ensures the temperature uniformity of the entire cooling structure hot wall 101.

[0038] In one embodiment, the segments of each second cooling channel 106 within each first cooling channel 105 are all zigzag ribs, see... Figure 2 and Figure 3 Each of the second cooling channels 106 is tightly attached to the hot wall 101 of the cooling structure, see Figure 4 .

[0039] Since the segments of each second cooling channel 106 within each first cooling channel 105 are all zigzag ribs, the zigzag ribs within each first cooling channel 105 cooperate to form a zigzag rib turbulence structure within the corresponding first cooling channel 105. Consequently, the cooling gas within each first cooling channel 105 flows more tortuously under the action of the zigzag ribs, resulting in stronger turbulence. This further enhances the heat exchange between the cooling structure hot wall 101 and the cooling gas, and further improves the cooling efficiency of the cooling structure hot wall 101.

[0040] Since each of the second cooling channels 106 is tightly attached to the hot wall 101 of the cooling structure, the second layer of cooling components formed by the multiple second cooling channels 106 adopts an internal cooling method that is closer to the hot wall 101 of the cooling structure. Similarly, the first layer of cooling components formed by the multiple first cooling channels 105 adopts an internal cooling method that is close to the hot wall 101 of the cooling structure. Therefore, the cooling structure 1 makes the hot wall 101 of the cooling structure have a high cooling efficiency.

[0041] Among them, such as Figure 2 and Figure 3 As shown, the segments of each second cooling channel 106 within each first cooling channel 105 are V-shaped zigzag ribs.

[0042] Preferably, such as Figure 3 As shown, the V-shaped openings of each V-shaped rib in each first cooling channel 105 are all oriented towards the cooling gas flow direction in the corresponding first cooling channel 105; the orthographic projection of the vertex of each V-shaped rib in each first cooling channel 105 is all on the central axis of the corresponding first cooling channel 105.

[0043] In this way, the V-shaped ribs in each first cooling channel 105 cause more intense disturbance to the cooling gas in the corresponding first cooling channel 105, resulting in stronger turbulence. This further enhances the heat exchange between the cooling structure hot wall 101 and the cooling gas, and further improves the cooling efficiency of the cooling structure hot wall 101.

[0044] In one embodiment, such as Figure 2 and Figure 3 As shown, the opening size of each first cooling channel 105 is equal, the opening size of each second cooling channel 106 is equal, and the multiple second cooling channels 106 are distributed at equal intervals. This further ensures the temperature uniformity of the entire cooling structure's hot wall 101.

[0045] like Figures 5-9As shown, a heat insulation tile for a combustion chamber in a gas turbine includes a heat insulation tile hot wall 201 facing the flame inside the combustion chamber and a heat insulation tile cold wall 202 facing the combustion chamber shell. A first outer peripheral wall 203 for facing the combustion chamber shell is connected around the outer edge of the heat insulation tile hot wall 201, and a second outer peripheral wall 204 for facing the combustion chamber shell is connected around the outer edge of the heat insulation tile cold wall 202. The ends of the first outer peripheral wall 203 and the second outer peripheral wall 204 for facing the combustion chamber shell are connected by a connecting wall 205. The first outer peripheral wall 203, the second outer peripheral wall 204, the heat insulation tile hot wall 201 and the connecting wall 205 form a cooling gas chamber 206.

[0046] It also includes the aforementioned cooling structure based on staggered countercurrent flow and rib turbulence. The cooling structure 1 is arranged between the heat insulation tile hot wall 201 and the heat insulation tile cold wall 202, and the heat insulation tile hot wall 201 forms the cooling structure hot wall 101, and the heat insulation tile cold wall 202 forms the cooling structure cold wall 102. One end of each first cooling channel 105 is connected to the cooling gas chamber 206 and the other end is connected to the outside through the first outer peripheral wall 203. One end of each second cooling channel 106 is connected to the cooling gas chamber 206 and the other end is connected to the outside through the first outer peripheral wall 203 or the second outer peripheral wall 204.

[0047] The cooling gas introduced into the cooling gas chamber 206 enters each of the first cooling channels 105 and each of the second cooling channels 106. After heat exchange with the heat insulation tile hot wall 201, the cooling gas in each of the first cooling channels 105 is discharged to the outside through the first outer peripheral wall 203. After heat exchange with the heat insulation tile hot wall 201, the cooling gas in each of the second cooling channels 106 is discharged to the outside through the first outer peripheral wall 203 or the second outer peripheral wall 204. By arranging the cooling structure 1 between the heat insulation tile hot wall 201 and the heat insulation tile cold wall 202, this utility model can improve the cooling efficiency of the heat insulation tile hot wall 201 and ensure the temperature uniformity of the entire heat insulation tile hot wall 201. In addition, the heat insulation tile 2 including the cooling structure 1 can greatly reduce the dimensional requirements in the thickness direction. Furthermore, the cooling structure 1 can also fully cool the heat insulation tile cold wall 202 to ensure the safe use of the heat insulation tile 2.

[0048] In one embodiment,

[0049] like Figures 6-9 As shown, there are two heat insulation tile cold walls 202 distributed at a certain distance. Each heat insulation tile cold wall 202 is connected to a second outer peripheral wall 204. The connecting wall 205 is connected to the first outer peripheral wall 203 and the two second outer peripheral walls 204. There are two cooling structures 1, and each cooling structure 1 is arranged between the heat insulation tile hot wall 201 and one of the heat insulation tile cold walls 202.

[0050] Preferably, such as Figure 6 and Figure 7 As shown, the heat insulation tile 2 also includes a hollow fastening housing 207 with one open end. The open end of the fastening housing 207 is connected to the corresponding positions of the two heat insulation tile cold walls 202, the two second outer peripheral walls 204, and the connecting wall 205. The inner cavity 20701 of the fastening housing 207 is connected to the cooling gas chamber 206. The fastening housing 207 is provided with a heat insulation tile mounting channel 208 for oriented towards the combustion chamber shell. One end of the heat insulation tile mounting channel 208 passes through the heat insulation tile hot wall 201 and the other end passes through the shell wall 20702 of the fastening housing 207 for being adjacent to the combustion chamber shell. The shell wall 20702 of the fastening housing 207 is provided with an air inlet 209.

[0051] The heat insulation tile 2 can be fixed to the combustion chamber shell by means of the heat insulation tile mounting hole 208. The cooling gas can be introduced into the inner cavity 20701 of the fastening shell 207 by means of the air inlet 209. The cooling gas introduced into the inner cavity 20701 of the fastening shell 207 further enters the cooling gas chamber 206. The cooling gas in the cooling gas chamber 206 enters each first cooling channel 105 of each cooling structure 1 and then enters each second cooling channel 106 of each cooling structure 1. After heat exchange with the heat insulation tile hot wall 201, the cooling gas in each first cooling channel 105 is discharged to the outside through the first outer peripheral wall 203. After heat exchange with the heat insulation tile hot wall 201, the cooling gas in each second cooling channel 106 is discharged to the outside through the first outer peripheral wall 203 or the second outer peripheral wall 204.

[0052] Among them, the heat insulation tile 2 is generally formed in one piece using 3D printing technology.

[0053] The cooling gas used in this heat insulation tile 2 comes from the outlet air of the compressor in the gas turbine.

[0054] A combustion chamber for a gas turbine includes a combustion chamber shell and the aforementioned heat insulation tile for the combustion chamber in a gas turbine. The heat insulation tile 2 is fixed to the combustion chamber shell by fastening screws passing through the heat insulation tile mounting hole 208.

[0055] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present utility model, and these improvements and substitutions should also be considered within the protection scope of the present utility model.

Claims

1. A cooling structure based on staggered countercurrent flow and finned turbulence, characterized in that: The system includes a high-temperature cooling structure hot wall (101) and a low-temperature cooling structure cold wall (102). Between the hot wall (101) and the cold wall (102), there are multiple parallel and adjacent first cooling channels (105) and multiple spaced second cooling channels (106). Each second cooling channel (106) is a zigzag channel and is sequentially inserted into the multiple first cooling channels (105). The segments of each second cooling channel (106) in each first cooling channel (105) cooperate to form a ribbed flow-disrupting structure. The cooling gas in two adjacent first cooling channels (105) flows in opposite directions, and the cooling gas in two adjacent second cooling channels (106) flows in opposite directions.

2. The cooling structure based on staggered countercurrent flow and finned turbulence according to claim 1, characterized in that: Each segment of the second cooling channel (106) within each of the first cooling channels (105) is a zigzag rib, and each of the second cooling channels (106) is tightly attached to the hot wall (101) of the cooling structure.

3. A cooling structure based on staggered countercurrent flow and rib turbulence according to claim 2, characterized in that: Each segment of the second cooling channel (106) within each of the first cooling channels (105) is a V-shaped zigzag rib.

4. A cooling structure based on staggered countercurrent flow and rib turbulence according to claim 3, characterized in that: The V-shaped openings of each V-shaped rib in each of the first cooling channels (105) face the direction of cooling gas flow in the corresponding first cooling channel (105).

5. A cooling structure based on staggered countercurrent flow and rib turbulence according to claim 4, characterized in that: The orthographic projection of the vertex of each V-shaped rib within each of the first cooling channels (105) lies on the central axis of the corresponding first cooling channel (105).

6. A cooling structure based on staggered countercurrent flow and finned turbulence according to claim 1, characterized in that: The opening size of each of the first cooling channels (105) is equal, the opening size of each of the second cooling channels (106) is equal, and the plurality of second cooling channels (106) are distributed at equal intervals.

7. A heat-insulating tile for the combustion chamber of a gas turbine, characterized in that: It includes a heat-insulating tile hot wall (201) facing the flame inside the combustion chamber and a heat-insulating tile cold wall (202) facing the combustion chamber shell. The outer edge of the heat-insulating tile hot wall (201) is connected to a first outer peripheral wall (203) for facing the combustion chamber shell, and the outer edge of the heat-insulating tile cold wall (202) is connected to a second outer peripheral wall (204) for facing the combustion chamber shell. The first outer peripheral wall (203) and the second outer peripheral wall (204) for facing the combustion chamber shell are connected by a connecting wall (205). The first outer peripheral wall (203), the second outer peripheral wall (204), the heat-insulating tile hot wall (201) and the connecting wall (205) form a cooling gas chamber (206). It also includes a cooling structure based on staggered counterflow and rib turbulence as described in any one of claims 1-6, wherein the cooling structure (1) is arranged between the heat insulation tile hot wall (201) and the heat insulation tile cold wall (202), and the heat insulation tile hot wall (201) forms the cooling structure hot wall (101), and the heat insulation tile cold wall (202) forms the cooling structure cold wall (102), one end of each first cooling channel (105) is connected to the cooling gas chamber (206) and the other end is connected to the outside through the first outer peripheral wall (203), and one end of each second cooling channel (106) is connected to the cooling gas chamber (206) and the other end is connected to the outside through the first outer peripheral wall (203) or the second outer peripheral wall (204).

8. A heat-insulating tile for a combustion chamber in a gas turbine according to claim 7, characterized in that: The heat insulation tile cold wall (202) consists of two and is distributed at a certain distance. Each heat insulation tile cold wall (202) is connected to a second outer peripheral wall (204). The connecting wall (205) is connected to the first outer peripheral wall (203) and the two second outer peripheral walls (204). There are two cooling structures (1), and each cooling structure (1) is arranged between the heat insulation tile hot wall (201) and one of the heat insulation tile cold walls (202).

9. A heat-insulating tile for a combustion chamber in a gas turbine according to claim 8, characterized in that: It also includes a hollow fastening housing (207) with one open end. The open end of the fastening housing (207) is connected to the corresponding positions of the two heat insulation tile cold walls (202), the two second outer peripheral walls (204), and the connecting wall (205). The inner cavity (20701) of the fastening housing (207) is connected to the cooling gas chamber (206). The fastening housing (207) is provided with a heat insulation tile mounting channel (208) for oriented towards the combustion chamber shell. One end of the heat insulation tile mounting channel (208) penetrates the heat insulation tile hot wall (201), and the other end penetrates the shell wall (20702) of the fastening housing (207) for being adjacent to the combustion chamber shell. The shell wall (20702) of the fastening housing (207) is provided with an air inlet (209).

10. A combustion chamber for a gas turbine, comprising a combustion chamber shell, characterized in that: It also includes the heat insulation tile for the combustion chamber in a gas turbine as described in claim 9, wherein the heat insulation tile (2) is fixed to the combustion chamber shell by fastening screws passing through the heat insulation tile mounting hole (208).

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